Outer premix barrel vent air sweep

ABSTRACT

A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.

TECHNICAL FIELD

The present disclosure generally pertains to gas turbine engines, and is more particularly directed toward a fuel injector with an outer premix barrel.

BACKGROUND

Gas turbine engines include compressor, combustor, and turbine sections. Fuel for gas turbine engines may accumulate on or adjacent to injector surfaces during gas turbine engine operation, which may lead to auto-ignition or flame holding.

G.B. patent No. 1,320,263 discloses an air swirler for use in the head end of a gas turbine combustion chamber comprising: an annular body portion having an upstream face and a downstream face normal to the axis thereof and defining a central hole for accommodation therein of a fuel nozzle, and a plurality of angled blade members disposed about the circumference of said body and forming slots for the passage of air there-between, the ratio of the dimension of each blade face between its leading and trailing edges to the width of the slots being within the range of 1.15 to 1.85. A plurality of air sweeper holes may extend generally from the slots to the downstream face of the body portion so that a portion of the air will flow through the air sweeper holes and sweep the face of the fuel nozzle.

The present disclosure is directed toward overcoming one or more of the problems discovered by the inventors.

SUMMARY OF THE DISCLOSURE

A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.

A method for overhauling a gas turbine engine injector is also disclosed. The method includes removing an outer premix barrel from the injector. The outer premix barrel includes a barrel and a barrel end. The barrel includes a body portion including vent air inlets, a barrel portion extending axially aft from the body portion, and a plurality of vanes extending axially forward from the body portion. Each vane includes a truncated wedge shape and a plurality of vent passages in flow communication with at least one vent air inlet. Each vent passage exits the vane at an inward surface located at a truncated portion of the truncated wedge shape. The barrel end is joined to the barrel at an aft end of the barrel portion. The barrel end includes a cylindrical tube shape. The method also includes separating the barrel end from the barrel. The method further includes joining a new barrel end to the barrel with a metal joining process.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of an exemplary gas turbine engine.

FIG. 2 is a perspective view of the injector of FIG. 1.

FIG. 3 is a cross-sectional view of the injector head of FIG. 2.

FIG. 4 is a perspective view of the forward end of the outer premix barrel of FIG. 3.

FIG. 5 is a perspective view of the aft end of the outer premix barrel of FIG. 4.

FIG. 6 is an exploded view of the injector head of FIG. 3.

FIG. 7 is a flowchart of a method for overhauling the injector of FIG. 2.

DETAILED DESCRIPTION

The systems and methods disclosed herein include a gas turbine engine injector including an outer premix barrel. In embodiments, the outer premix barrel includes vanes with a truncated wedge shape and is removable from the injector head. Each vane includes vent passages at the inward surface, the radially innermost portion of the truncated wedge shape. During operation of the gas turbine engine the vent passages may sweep away fuel that may collect in a low pressure area adjacent inward surface, which may prevent auto-ignition or flame holding. A removable outer premix barrel may facilitate access to other components within the injector and may facilitate overhaul of the outer premix barrel.

FIG. 1 is a schematic illustration of an exemplary gas turbine engine. Some of the surfaces have been left out or exaggerated (here and in other figures) for clarity and ease of explanation. Also, the disclosure may reference a forward and an aft direction. Generally, all references to “forward” and “aft” are associated with the flow direction of primary air (i.e., air used in the combustion process), unless specified otherwise. For example, forward is “upstream” relative to primary air flow, and aft is “downstream” relative to primary air flow.

In addition, the disclosure may generally reference a center axis 95 of rotation of the gas turbine engine, which may be generally defined by the longitudinal axis of its shaft 120 (supported by a plurality of bearing assemblies 150). The center axis 95 may be common to or shared with various other engine concentric components. All references to radial, axial, and circumferential directions and measures refer to center axis 95, unless specified otherwise, and terms such as “inner” and “outer” generally indicate a lesser or greater radial distance from, wherein a radial 96 may be in any direction perpendicular and radiating outward from center axis 95.

A gas turbine engine 100 includes an inlet 110, a shaft 120, a gas producer or “compressor” 200, a combustor 300, a turbine 400, an exhaust 500, and a power output coupling 600. The gas turbine engine 100 may have a single shaft or a dual shaft configuration.

The compressor 200 includes a compressor rotor assembly 210, compressor stationary vanes (“stators”) 250, and inlet guide vanes 255. The compressor rotor assembly 210 mechanically couples to shaft 120. As illustrated, the compressor rotor assembly 210 is an axial flow rotor assembly. The compressor rotor assembly 210 includes one or more compressor disk assemblies 220. Each compressor disk assembly 220 includes a compressor rotor disk that is circumferentially populated with compressor rotor blades. Stators 250 axially follow each of the compressor disk assemblies 220. Each compressor disk assembly 220 paired with the adjacent stators 250 that follow the compressor disk assembly 220 is considered a compressor stage. Compressor 200 includes multiple compressor stages. Inlet guide vanes 255 axially precede the compressor stages.

The combustor 300 includes one or more injectors 310 and includes one or more combustion chambers 390. Each injector 310 includes an injector head 320 (shown in FIGS. 2 and 3), which includes an outer premix barrel 330 (shown in FIGS. 3-6). In the gas turbine engine shown, each injector 310 is installed into combustor 300 in the axial direction relative to center axis 95 through radial case portion 399 of compressor combustor case 398 or the compressor diffuser case.

The turbine 400 includes a turbine rotor assembly 410, and turbine nozzles 450. The turbine rotor assembly 410 mechanically couples to the shaft 120. As illustrated, the turbine rotor assembly 410 is an axial flow rotor assembly. The turbine rotor assembly 410 includes one or more turbine disk assemblies 420. Each turbine disk assembly 420 includes a turbine that is circumferentially populated with turbine blades. Turbine nozzles 450 axially precede each of the turbine disk assemblies 420. Each turbine disk assembly 420 paired with the adjacent turbine nozzles 450 that precede the turbine disk assembly 420 is considered a turbine stage. Turbine 400 includes multiple turbine stages.

The exhaust 500 includes an exhaust diffuser 520 and an exhaust collector 550.

FIG. 2 is a perspective view of injector 310 of FIG. 1. Injector 310 may include a flange 317, an injector head 320, a first main gas tube 311, a second main gas tube 312, a support tube 313, a liquid inlet tube stem 314, a liquid inlet tube 354, a pilot stem 316, and a liquid pilot tube assembly 370. Flange 317 may be a cylindrical disk. Flange 317 includes flange bolt holes 319 for securing injector 310 to gas turbine engine 100 at radial case portion 399 (shown in FIG. 1). Flange 317 may also include handles 318. Fittings 379 such as gas main and liquid main connector assemblies may attach to divider blocks, such as main gas divider block 386, attached to an outer or base surface of flange 317. Liquid and gas fuel sources may be attached to the fittings 379.

Injector head 320 may include an assembly axis 309 (shown in FIG. 3). All references to radial, axial, and circumferential directions and measures of injector head 320 and the elements of injector head 320 refer to assembly axis 309, and terms such as “inner” and “outer” generally indicate a lesser or greater radial distance from assembly axis 309. The center of flange 317 may be offset from assembly axis 309.

FIG. 3 is a cross-sectional view of the injector head 320 of FIG. 2. Referring to FIGS. 2 and 3, injector head 320 may include body assembly 321, outer cap 315, outer premix barrel 330, inner premix tube 360, premix barrel cap 324, liquid gallery assembly 340, flow shield 392, retaining ring 355, liquid pilot tube assembly 370, and pilot shroud 380. Body assembly 321 may include injector body 322 and gas main shroud 323. Injector body 322 may have a disk or cylindrical shaped base with a coaxial hollow cylinder portion extending in the aft direction from the base. The diameter of the hollow cylinder portion may be larger than the diameter of the base.

Referring to FIG. 3, injector body 322 may include liquid pilot opening 326, feed air passages 325, liquid main opening 327, collar counterbore 328, and retaining ring recess 329. Liquid pilot opening 326 may be coaxial to injector body 322 and may extend through the base of injector body 322 in the axial direction. Feed air passages 325 may also extend through the base of injector body 322 in the axial direction. Feed air passages 325 may be located radially outward from assembly axis 309 and liquid pilot opening 326, and may be located radially inward from an inner surface of the hollow cylinder portion of injector body 322. In embodiments, injector body 322 includes four feed air passages 325.

Liquid main opening 327 may be located radially outward from assembly axis 309 and feed air passages 325, and may be located radially inward from the inner surface of the hollow cylinder portion of injector body 322. Collar counterbore 328 is coaxial to liquid main opening 327 and extends in the forward direction partially into the base of injector body 322 from the aft side of the base.

Retaining ring recess 329 is an annular recess may be located at the aft end of the hollow cylinder portion of injector body 322. Retaining ring recess 329 may be threaded or may include a lip or an annular protrusion configured to hold retaining ring 355 in place.

Referring again to FIGS. 2 and 3, gas main shroud 323 may have a hollow cylinder shape and may have a ‘C’, ‘U’, or ‘J’ shaped cross-section revolved about injector assembly axis 309. Gas main shroud 323 may include fuel transfer bosses 308. Fuel transfer bosses 308 may be thickened portions or boss structures extending from a radially inner portion of the hollow cylinder shape of gas main shroud 323. Fuel transfer bosses 308 may be formed to include fuel transfer passages. One end of the ‘C’, ‘U’, or ‘J’ shape may attach to the hollow cylinder portion of injector body 322 at or near a radially outermost portion of the hollow cylinder portion of injector body 322, while the other end of the ‘C’, ‘U’, or ‘J’ shape may attach to the base of injector body 322 at or near a radially outermost portion of the base. The connection of the ‘U’ or ‘J’ shape of gas main shroud 323 to injector body 322 may form an annular chamber between gas main shroud 323 and injector body 322. Injector body 322 and gas main shroud 323 may be brazed or welded together.

Outer cap 315 may be a dome shaped cap that attaches to the body assembly 321 at the radially outer surface of gas main shroud 323. Outer cap 315 may include multiple holes and passageways.

Referring again to FIG. 2, first main gas tube 311 and second main gas tube 312 may extend from the gas main connector assembly (not shown) and flange 317 in the axial direction to fuel transfer bosses 308 (shown in FIG. 3). First main gas tube 311 and second main gas tube 312 may be in flow communication with main gas shroud and the flow transfer holes.

Support tube 313 may connect to flange 317 and gas main shroud 323 of body assembly 321. Support tube 313 may extend axially and radially inward from flange 317 to body assembly 321 relative to injector assembly axis 309.

Liquid inlet tube stem 314 and pilot stem 316 may each extend from flange 317 to injector head 320 in the axial direction. Liquid inlet tube stem 314 may be a circular tube and may attach to gas main shroud 323. Liquid inlet tube stem 314 may attach to gas main shroud 323 near or adjacent to where support tube 313 connects to gas main shroud 323. Pilot stem 316 may attach to and may be partially inserted into liquid pilot opening 326 of injector body 322. Liquid inlet tube stem 314 may be welded or brazed to gas main shroud 323, and pilot stem 316 may be welded or brazed to injector body 322.

Liquid inlet tube 354 may extend axially through liquid inlet tube stem 314 from the liquid main connector and flange 317 to injector body 322 and through liquid main opening 327 of injector body 322.

Referring to FIG. 3, liquid gallery assembly 340 may include collar 353, gallery cover 342, liquid gallery 341, atomizers (not shown), and clocking pin 352. Liquid inlet tube 354 may connect to gallery cover 342. Collar 353 may be located adjacent gallery cover 342 around the end of liquid inlet tube 354 that attaches or connects to gallery cover 342. Collar 353 may be also located within collar counterbore 328.

Liquid gallery 341 includes gallery body and liquid gallery scroll 343. Liquid gallery 341 may also include atomizer inlets (not shown), atomizer bosses 347, and clocking pin boss 348. Gallery body may be an annular ring or hollow cylinder coaxial to liquid gallery assembly 340 and injector assembly axis 309. Liquid gallery 341 is formed to include liquid gallery scroll 343, an annular channel about the forward radial surface of gallery body and extending into gallery body. Liquid gallery scroll 343 may be sized to maintain a predetermined velocity of the liquid fuel passing through liquid gallery scroll 343 during operation of the gas turbine engine 100.

In the embodiment illustrated, the cross-section of liquid gallery scroll 343 is an extended half round or rectangle with a semicircle at the end. Other cross-sectional shapes such as rectangles, squares, and circles may also be used. The edges of the rectangle and square cross-sections may be rounded.

Atomizer bosses 347 may extend from the aft radial surface of the annular ring or hollow cylinder shape of liquid gallery 341 in the axially aft direction. Each atomizer boss 347 may be sized to hold one atomizer. Each atomizer boss 347 may have a hollow cylinder shape with a diameter smaller than the radial thickness of liquid gallery 341. Atomizer bosses 347 may be equally spaced about liquid gallery 341.

In the embodiment illustrated, a clocking pin boss 348 extends from the aft radial surface of the annular ring or hollow cylinder shape of liquid gallery 341 in the axially aft direction between two atomizer bosses 347. Clocking pin boss 348 may be shaped similarly to atomizer bosses 347 and may be sized to hold clocking pin 352. Clocking pin 352 may have a cylindrical shape. Clocking pin 352 may help align inner premix tube 360 within injector head 320.

Gallery cover 342 may be an annular ring or hollow cylinder with a ‘C’ or ‘U’ shaped cross-section revolved around the axis of liquid gallery assembly 340 which is coaxial to injector assembly axis 309. Gallery cover 342 may include liquid inlet tube boss 349 extending axially forward from the annular ring or hollow cylinder shape of gallery cover 342. Liquid inlet tube 354 extends into liquid inlet tube boss 349. Collar 353 may be located radially around liquid inlet tube boss 349.

Gallery cover 342 may be sized to fit over the outer and inner circumferential surfaces of liquid gallery 341. The forward radial surface of liquid gallery 341 may contact gallery cover 342 and form a seal with gallery cover 342. Gallery cover 342 may be brazed or welded to liquid gallery 341 at the outer and inner circumferential surfaces of liquid gallery 341.

Flow shield 392 may include an axial portion located radially inward from liquid gallery 341 and a radial portion extending from the axial portion located axially between liquid gallery 341 and inner premix tube 360.

Inner premix tube 360 may include transition end 361, middle tube 362, tip end 363, and premix tube inner surface 365. In the embodiment illustrated in FIG. 3, transition end 361 is a hyperbolic funnel that includes an annular disk portion 367 and a redirection portion 368 that curves toward the axially aft direction from the annular disk portion 367. In other embodiments, redirection portion may be formed from various cross-sectional shapes revolved about the axis of inner premix tube 360 that extend radially inward and axially from the annular disk portion 367 to begin the transition from a radial direction to an axial direction.

Transition end 361 may include outer cylindrical portion 375, retaining lip 364, clocking hole 369, and wipe passages 366. Outer cylindrical portion 375 may extend axially forward from the radially outer part of annular disk portion 367 in the direction opposite tip end 363. Outer cylindrical portion 375 may have a right hollow circular cylinder shape. Retaining lip 364 may extend radially outward from outer cylindrical portion. In the embodiment illustrated, retaining lip 364 also extends axially forward. Clocking hole 369 is sized to receive clocking pin 352 and aligns with clocking pin 352 when assembled. Transition end 361 may include a thickened or boss portion around clocking hole 369.

Transition end 361 is configured to include wipe passages 366. Wipe passages 366 may extend through redirection portion 368. Wipe passages 366 are configured to direct air along premix tube inner surface 365. In the embodiment shown, transition end 361 includes 12 wipe passages 366 equally spaced thirty degrees apart about transition end 361 extending axially through transition end 361. In other embodiments, a different number of wipe passages 366 may be used. Wipe passages 366 are sized and configured so that there is no or a minimal pressure drop across the wipe passage 366. Different shapes, sizing, spacing, and configurations may also be used.

Middle tube 362 may be welded or brazed to the aft end of transition end 361. In the embodiment shown in FIG. 3, middle tube 362 continues the hyperbolic funnel shape of transition end 361. In other embodiments, middle tube 362 may be a conical frustum, a funnel, or formed from a cross-section with curved outer and inner surfaces revolved about the axis of inner premix tube 360.

Tip end 363 may be welded or brazed to the aft end of middle tube 362. In the embodiment shown in FIG. 3, tip end 363 includes a curved portion 357, a cylindrical portion 358, and a tip face 359. Curved portion 357 may continue the hyperbolic funnel shape of transition end 361 and middle tube 362 and transitions from the curve of middle tube to a hollow right circular cylinder. Cylindrical portion 358 may be a hollow right circular cylinder extending aft from curved portion 357. Tip face 359 extends radially inward from the aft end of cylindrical portion 358 and may form an annular disk, the aft end being the axial end of cylindrical portion 358 distal to transition end 361.

Premix tube inner surface 365 is at least a portion of the outer surface of inner premix tube 360. Premix tube inner surface 365 is a revolved surface about the axis of inner premix tube 360 that transitions from a radial or an annular ring surface to a circumferential or cylindrical surface. In the embodiment illustrated, premix tube inner surface 365 is a hyperbolic funnel or a segment of a pseudosphere. In other embodiments, the radial surface may transition to a cylindrical surface with a combination of line segments or curves revolved about the axis of inner premix tube 360.

In the embodiment illustrated in FIG. 3, retaining ring 355 is an annular ring. Retaining ring 355 is sized to be installed within retaining ring recess 329. In the embodiment shown, retaining ring 355 and retaining ring recess 329 are threaded to secure retaining ring 355 to injector body 322. Other retaining or locking mechanisms may be used to secure retaining ring 355 to injector body 322. Retaining ring 355 is configured to secure, retain, or lock inner premix tube 360 within injector head 320. In the embodiment shown, retaining ring 355 is axially aft and radially aligned with retaining lip 364, securing inner premix tube 360 to injector body 322.

Liquid pilot tube assembly 370 may extend axially through pilot stem 316 from the pilot connector and through injector head 320. Liquid pilot tube assembly 370 may be coaxial to injector assembly axis 309. Pilot shroud 380 may be located radially outward from a portion of liquid pilot tube assembly 370 and located radially inward from inner premix tube 360. Pilot shroud 380 may extend aft from injector body 322.

FIG. 4 is a perspective view of the forward end of the outer premix barrel 330 of FIG. 3. FIG. 5 is a perspective view of the aft end of the outer premix barrel of FIG. 4. Referring to FIGS. 3-5, outer premix barrel 330 may include barrel 331, barrel end 332, and premix tube outer surface 339. Barrel 331 may include body portion 337, barrel portion 338, and vanes 333. In the embodiment illustrated, body portion 337 generally has an annular disk shape. Referring to FIG. 5, body portion 337 includes vent air inlets 335 and bolt holes 385. Vent air inlets 335 may extend through the annular disk shape in the axial direction. In the embodiment illustrated, vent air inlets 335 extend through the annular disk shape from an aft radial face of the annular disk shape. Barrel portion 338 may extend axially aft from body portion 337. Barrel portion 338 may extend from the aft and radially inner portion of body portion 337. Barrel portion 338 may have a hollow cylinder or cylindrical tube shape. The hollow cylinder or cylindrical tube shape may be tapered. The tapered cylinder may be the frustum of a hollow cone.

Referring to FIG. 4, vanes 333 may extend axially forward from body portion 337. In the embodiment illustrated, vanes 333 are wedge shaped with the tip of the wedge truncated or removed. The edges of vanes 333 may be rounded. Vanes 333 may include other shapes configured to direct and swirl air into the premix tube. Each vane 333 may include inward surface 387, outer surface 395, contact surface 396, first inlet surface 393, and second inlet surface 394. Inward surface 387 is the surface at the end of each vane 333 and is the radially inner surface of vane 333. Inward surfaces 387 may be the surface located at the truncated portion of the vanes 333. In the embodiment illustrated, each inward surface 387 is a circumferential surface. In other embodiments, each inward surface 387 may be a flat or rounded surface.

Outer surface 395 may be the radially outer surface of each vane 333, the surface opposite inward surface 387. Outer surface 395 may be flat or rounded and may be a circumferential surface. Contact surface 396 may be the surface distal to and opposite body portion 337. Contact surface 396 may face the axial direction extending from inward surface 387 to outer surface 395. Contact surface 396 may contact injector body 322 when outer premix barrel 330 is connected to injector body 322.

First inlet surface 393 and second inlet surface 394 may be radial surfaces on opposite sides of each vane 333. Both first inlet surface 393 and second inlet surface 394 may extend from outer surface 395 to inward surface 387. Vanes 333 are spaced apart to form primary air inlets 336. The first inlet surface 393 and the second inlet surface 394 of adjacent vanes 333 may form a primary air inlet 336.

Referring to FIGS. 4 and 5, each vane 333 may include vent passages 334, fuel passages 383, fuel supply passages 384, vent air inlets 335, and bolt holes 385. Vent passages 334 may extend partially through each vane 333 and exit vane 333 at inward surface 387. In the embodiment illustrated, each vane 333 includes six vent passages 334. A vent air inlet 335 extends into a vane 333 and may extend through body portion 337 toward contact surface 396. In the embodiment shown, each vent passage 334 (examples shown dashed) extend from vent air inlet 335 (example also shown dashed) to inward surface 387. Each vent air passage 334 is in flow communication with at least one vent air inlet 335.

A fuel supply passage 384 extends axially into each vane 333. Each fuel supply passage 384 may extend from contact surface 396 towards body portion 337. Fuel passages 383 may extend from a fuel supply passage 384 to a first inlet surface 393 or a second inlet surface 394, adjacent primary air inlet 336. In the embodiment illustrated, each vane 333 includes six fuel passages 383 located at the radially outer portion of first inlet surface 393. Each fuel supply passage 384 is in flow communication with the fuel passages 383 located on the same vane 333 as the fuel supply passage 384.

Referring to FIG. 5, barrel end 332 may be joined to barrel 331 at the aft end of barrel portion 338 with a metal joining process such as welding or brazing. In one embodiment, barrel end 332 is joined to barrel 331 by electron beam welding. Barrel end 332 may have a hollow cylinder or cylindrical tube shape similar to the shape of barrel portion 338. The hollow cylinder or cylindrical tube shape may be tapered. The tapered cylinder may be the frustum of a hollow cone. Premix barrel cap 324 may be welded or brazed to the aft end of barrel end 332 at the outer surface of barrel end 332. Referring to FIG. 3, premix barrel cap 324 may have a ‘C’, ‘U’, or ‘J’ shaped cross-section that is revolved about injector assembly axis 309. Premix barrel cap 324 may form an air pocket or channel with barrel end 332.

Premix tube outer surface 339 may include the radially inner cylindrical surfaces of barrel 331 and barrel end 332. When installed in injector head 320 (shown in FIG. 3), premix tube outer surface 339 may be located radially outward from premix tube inner surface 365.

FIG. 6 is an exploded view of the injector head 320 of FIG. 3. Referring to FIGS. 3 and 6, outer premix barrel 330 may be secured to body assembly 321 with bolts 389 and lock plates 388. Inner premix tube 360 may be secured to body assembly 321 by retaining ring 355. In some embodiments, retaining ring 355 is screwed on to body assembly 321.

One or more of the above components (or their subcomponents) may be made from stainless steel and/or durable, high temperature materials known as “superalloys”. A superalloy, or high-performance alloy, is an alloy that exhibits excellent mechanical strength and creep resistance at high temperatures, good surface stability, and corrosion and oxidation resistance. Superalloys may include materials such as HASTELLOY, INCONEL, WASPALOY, RENE alloys, HAYNES alloys, INCOLOY, MP98T, TMS alloys, and CMSX single crystal alloys.

INDUSTRIAL APPLICABILITY

Gas turbine engines may be suited for any number of industrial applications such as various aspects of the oil and gas industry (including transmission, gathering, storage, withdrawal, and lifting of oil and natural gas), the power generation industry, cogeneration, aerospace, and other transportation industries.

Referring to FIG. 1, a gas (typically air 10) enters the inlet 110 as a “working fluid”, and is compressed by the compressor 200. In the compressor 200, the working fluid is compressed in an annular flow path 115 by the series of compressor disk assemblies 220. In particular, the air 10 is compressed in numbered “stages”, the stages being associated with each compressor disk assembly 220. For example, “4th stage air” may be associated with the 4th compressor disk assembly 220 in the downstream or “aft” direction, going from the inlet 110 towards the exhaust 500). Likewise, each turbine disk assembly 420 may be associated with a numbered stage.

Once compressed air 10 leaves the compressor 200, it is diffused and enters the combustor 300. Referring to FIGS. 3 and 4, a portion of air 10 travels along path 306 and enters primary air inlets 336 between vanes 333 where fuel is added via fuel passages 383. Air 10 and the fuel are mixed and swirled between premix tube outer surface 339 and premix tube inner surface 365.

Referring to FIG. 1, the air 10 and fuel mixture is injected into the combustion chamber 390 and combusted. Energy is extracted from the combustion reaction via the turbine 400 by each stage of the series of turbine disk assemblies 420. Exhaust gas 90 may then be diffused in exhaust diffuser 520, collected and redirected. Exhaust gas 90 exits the system via an exhaust collector 550 and may be further processed (e.g., to reduce harmful emissions, and/or to recover heat from the exhaust gas 90).

Referring to FIG. 4, the truncated portion of each vane 333 may create a low pressure area or dead space at or adjacent to inward surface 387, which may cause some of the fuel passing through fuel passages 383 between vanes 333 and fuel from the atomizers to collect or accumulate on or adjacent inward surface 387. Fuel accumulated on or adjacent inward surface 387 may cause auto-ignition or flame holding.

Referring to FIGS. 3-5, during operation of gas turbine engine 100, a portion of the air 10 may travel along path 307 and enter vent air inlets 335. The air passes through vent air inlets 335 and exits vent air inlets 335 through vent passages 334. The air exiting vent passages 334 may provide a vent air sweep and push or sweep away the fuel accumulating in the low pressure area or dead space at or adjacent to inward surface 387. Sweeping the fuel out of the low pressure area or dead space may prevent auto-ignition and flame holding, which may increase efficiency, reduce emissions, and increase the life of injector head 320 including outer premix barrel 330 and inner premix tube 360.

During the lifetime of an injector 310, it may be overhauled. Components of injector head 320 including outer premix barrel 330, inner premix tube 360, and liquid gallery assembly 340 may need to be repaired or replaced. Referring to FIG. 6, outer premix barrel 330, including vanes 333, is removed from injector head 320 by removing bolts 389. Inner premix tube 360 is removed after removing outer premix barrel 330 by removing retaining ring 355. Removing outer premix barrel 330 and inner premix tube 360 provides access to liquid gallery assembly 340 (shown in FIG. 3), allowing the repair or replacement of liquid gallery assembly 340. Flow shield 392 (shown in FIG. 3) may also need to be removed to access liquid gallery assembly 340.

Referring to FIG. 3, liquid gallery assembly 340 may be welded or brazed to injector body 322. In embodiments, collar 353 is brazed into collar counterbore 328. Liquid gallery assembly 340 is removed from injector head 320 by machining out the portions of liquid gallery assembly 340 welded or brazed to injector body 322. Providing a removable outer premix barrel with vanes 333, a removable inner premix tube 360, and access to liquid gallery assembly 340 may reduce overhaul costs and may increase the life of injectors 310.

During operation of gas turbine engine 100 barrel end 332 of outer premix barrel 330 and tip end 363 of inner premix tube 360 are adjacent combustion chamber 390 and exposed to high temperatures. Barrel end 332 and tip end 363 may need to be replaced sooner than other portions of outer premix barrel 330 and inner premix tube 360. Replacing barrel end 332 or tip end 363 may reduce repair and overhaul costs of injectors 310.

FIG. 7 is a flowchart of a method for overhauling an injector 310. The method includes removing outer premix barrel 330 from the injector 310 at step 810. Step 810 includes removing bolts 389 that secure outer premix barrel 330 to injector body 322. Step 810 is followed by separating barrel end 332 from barrel 331 at step 820. Step 820 may include removing the weld or braze between barrel 331 and barrel end 332. Step 820 is followed by joining a new barrel end 332 to barrel 331 using a metal joining process. Metal joining processes such as welding and brazing may be used. In one embodiment, electron beam welding is used.

The preceding detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. The described embodiments are not limited to use in conjunction with a particular type of gas turbine engine. Hence, although the present disclosure, for convenience of explanation, depicts and describes a particular outer premix barrel, it will be appreciated that the outer premix barrel in accordance with this disclosure can be implemented in various other configurations, can be used with various other types of gas turbine engines, and can be used in other types of machines. Furthermore, there is no intention to be bound by any theory presented in the preceding background or detailed description. It is also understood that the illustrations may include exaggerated dimensions to better illustrate the referenced items shown, and are not consider limiting unless expressly stated as such. 

What is claimed is:
 1. An outer premix barrel for a fuel injector of a gas turbine engine, comprising: a body portion including vent air inlets; a barrel portion extending axially aft from the body portion; and a plurality of vanes extending axially forward from the body portion, each vane including an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface, each vent passage being in flow communication with at least one vent air inlet.
 2. The outer premix barrel of claim 1, wherein each vane is a truncated wedge shape and the inward surface of each vane is located at a truncated portion of the vane.
 3. The outer premix barrel of claim 1, wherein the body portion includes an annular disk shape.
 4. The outer premix barrel of claim 3, wherein each vent air inlet extends through the annular disk shape from a radial face of the annular disk shape and into one of the plurality of vanes towards a contact surface of the vane, the contact surface facing in an axial direction.
 5. The outer premix barrel of claim 4, wherein each vent passage extends from one of the vent air inlets to the inward surface located on the same vane as the vent air passage.
 6. The outer premix barrel of claim 1, wherein the barrel portion includes a hollow cylinder shape.
 7. The outer premix barrel of claim 1, wherein the plurality of vanes are spaced apart to form primary inlets, and each vane includes a fuel supply passage extending from a contact surface towards the body portion, the contact surface being an axial surface of the vane distal to the body portion, and a plurality of fuel passages on an inlet surface of the vane, adjacent one of the primary inlets, the plurality of fuel passages being in flow communication with the fuel supply passage.
 8. A fuel injector of a gas turbine engine, the fuel injector comprising: the outer premix barrel of claim 1; a body assembly including an injector body, the outer premix barrel being axially adjacent to the injector body and secured to the injector body; and an inner premix tube affixed to the injector body with a retaining ring, the inner premix tube being located radially inward from the outer premix barrel; wherein a premix tube outer surface including at least a portion of an inner surface of the outer premix barrel, and a premix tube inner surface including at least a portion of an outer surface of the inner premix tube form a premix tube.
 9. A gas turbine engine including the outer premix barrel of claim
 1. 10. A method for overhauling the outer premix barrel of claim 1, the method comprising: removing the outer premix barrel from an injector; separating the barrel end from the barrel; joining a new barrel end to the barrel with a metal joining process.
 11. A gas turbine engine outer premix barrel, comprising: a barrel including a body portion with an annular disk shape, the body portion including vent air inlets extending axially through the annular disk shape, a barrel portion extending axially aft from an aft and radially inner portion of the body portion, and a plurality of vanes extending from the body portion opposite the barrel portion, each vane including an inward surface located at an end of the vane and is a radially inner surface of the vane, and a plurality of vent passages in flow communication with at least one vent air inlet, each vent passage exiting the vane at the inward surface.
 12. The outer premix barrel of claim 11, wherein each of the plurality of vanes has a truncated wedge shape.
 13. The outer premix barrel of claim 11, further comprising a barrel end joined to the barrel at an aft end of the barrel portion, the barrel end including a shape of a frustum of a hollow cone.
 14. The outer premix barrel of claim 11, wherein each vent air inlet extends into one of the plurality of vanes toward a contact surface of the vane, the contact surface being distal to and opposite the body portion.
 15. The outer premix barrel of claim 11, wherein the plurality of vanes are spaced apart to form primary inlets, and each vane includes a fuel supply passage and a plurality of fuel passages extending from the fuel supply passage to an inlet surface adjacent one of the primary inlets, the plurality of fuel passages being in flow communication with the fuel supply passage.
 16. A gas turbine engine, comprising: a fuel injector including the outer premix barrel of claim 11; a body assembly including an injector body, wherein the outer premix barrel is secured to the injector body with bolts, and an inner premix tube affixed to the injector body with a retaining ring, the inner premix tube being located radially inward from the outer premix barrel.
 17. A method for overhauling a gas turbine engine injector, comprising: removing an outer premix barrel from the injector, the outer premix barrel including a barrel including a body portion including vent air inlets, a barrel portion extending axially aft from the body portion, and a plurality of vanes extending axially forward from the body portion, each vane including a truncated wedge shape and a plurality of vent passages in flow communication with at least one vent air inlet, each vent passage exits the vane at an inward surface located at a truncated portion of the truncated wedge shape, and a barrel end joined to the barrel at an aft end of the barrel portion, the barrel end including a cylindrical tube shape; separating the barrel end from the barrel; joining a new barrel end to the barrel with a metal joining process.
 18. The method of claim 17, wherein separating the barrel end from the barrel includes removing a weld from the barrel.
 19. The method of claim 17, wherein joining the new barrel end to the barrel with the metal joining process includes welding the new barrel end to the barrel.
 20. The method of claim 19, wherein welding the new barrel end to the barrel includes electron beam welding. 